Abrasive Coating and Manufacture and Use Methods

ABSTRACT

A method for applying an abrasive comprises: applying, to a substrate, the integral combination of: a self-braze material; an abrasive; and a matrix in which the abrasive is at least partially embedded; and heating to cause the self-braze material to braze to the substrate. The heating leaves at least a portion of the self-braze material with a composition comprising, in weight percent: cobalt 2.5-13.5; chromium 12-27; aluminum 5-7; yttrium 0.0-1.0; hafnium 0.0-1.0; silicon 1.0-3.0; tantalum 0.0-4.5; tungsten 0.0-6.5; rhenium 0.0-2.0; molybdenum 0.1-1.0; and the balance nickel.

CROSS-REFERENCE TO RELATED APPLICATION

Benefit is claimed of U.S. Patent Application Ser. No. 62/020,036, filed Jul. 2, 2014, and entitled “Abrasive Coating and Manufacture and Use Methods”, the disclosure of which is incorporated by reference herein in its entirety as if set forth at length.

BACKGROUND

The disclosure relates to abrasive coatings. More particularly, the disclosure relates to pre-formed abrasive coatings which may be applied to a substrate.

Gas turbine engines may have one or more nested spools of compressor sections and turbine sections co-rotating about an engine axis. An exemplary two-spool engine has: a low speed/pressure spool comprising a low speed/pressure compressor (LPC) and a low speed/pressure turbine (LPT); and a high speed/pressure spool comprising a high speed/pressure compressor (HPC) and a high speed/pressure turbine (HPT). The core flowpath of the engine passes air sequentially through the LPC and HPC to the combustor where it mixes with fuel and combusts. Combustion gases then proceed further downstream along the core flowpath through the HPT and LPT. Thus, the turbine sections may drive the rotation of their respective associated compressor sections. Optionally, one or more fan sections may be driven by the LPT or another turbine section. The fan sections drive air along a bypass flowpath, bypassing the core to produce additional thrust.

The individual compressor and turbine sections may be centrifugal or axial in configuration. In exemplary axial configurations, each section may have a number of stages. Each stage comprises an annular array or row (stage) of rotor blades. The blade stage may have an associated adjacent stage of stator vane airfoils. The airfoils are shaped to turn, accelerate and compress the working fluid flow in the compressor, and to generate lift for conversion to rotational energy in the turbine.

In a number of locations it may be desired to minimize clearance between relatively rotating components. A main example is the clearance between blade tips and the adjacent inner diameter (ID) surface of non-rotating structure. This ID surface is often formed by the ID surfaces of a circumferential array of blade outer air seal (BOAS) segments. The ID surface may be formed by an abradable ceramic coating on the ID surface of a metallic substrate of the BOAS segments. To interface with the abradable coating, the blade tips may bear an abrasive. The abrasive functions to abrade the abradable coating and provide a wear-in to a low radial clearance value between blade and BOAS. Low clearance means low blow-by of gas between tip and BOAS and thus high efficiency.

Many methods have been proposed for applying abrasive to blade tips. These include direct plating and direct spraying methods. Additionally, use of pre-formed abrasive has been proposed. U.S. Pat. No. 7,063,250 of Ohara et al., issued Jun. 20, 2006, discloses forming a squealer tip preform by plating an MCrAlY matrix and cubic boron nitride (CBN) abrasive to a brazing filler sheet. The preform is then brazed to the tip of a main airfoil substrate. U.S. Pat. No. 8,616,847 of Allen, issued Dec. 31, 2013, discloses forming a squealer tip preform by plating an MCrAlY matrix and cubic boron nitride (CBN) abrasive to a squealer tip preform. The preform is then brazed to the tip of a main airfoil substrate.

SUMMARY

One aspect of the disclosure involves a method for applying an abrasive. The method comprises: applying, to a substrate, the integral combination of a self-braze material; an abrasive and a matrix in which the abrasive is at least partially embedded; and heating to cause the self-braze material to braze to the substrate. The heating leaves at least a portion of the self-braze material with a composition comprising, in weight percent: cobalt 2.5-13.5; chromium 12-27; aluminum 5-7; yttrium 0.0-1.0; hafnium 0.0-1.0; silicon 1.0-3.0; tantalum 0.0-4.5; tungsten 0.0-6.5; rhenium 0.0-2.0; molybdenum 0.1-1.0; and the balance nickel.

A further embodiment of any of the foregoing embodiments may additionally and/or alternatively include said portion of the self-braze material having said composition comprising, in weight percent: cobalt 2.5-13.5; chromium 12-27; aluminum 5-7; yttrium 0.0-1.0; hafnium 0.0-1.0; silicon 1.0-3.0; tantalum 2.0-4.5; tungsten 2.0-6.5; rhenium 0.0-2.0; molybdenum 0.1-1.0; and the balance nickel.

A further embodiment of any of the foregoing embodiments may additionally and/or alternatively include said composition having no more than 1.0 weight percent of any other individual element.

A further embodiment of any of the foregoing embodiments may additionally and/or alternatively include said composition having no more than 3.0 weight percent of all other individual elements combined.

A further embodiment of any of the foregoing embodiments may additionally and/or alternatively include the matrix comprising an MCrAlY and the abrasive comprising cubic boron nitride.

A further embodiment of any of the foregoing embodiments may additionally and/or alternatively include the self-braze material comprising a sintered sheet of at least one first alloy of low melting point relative to the substrate and at least one second alloy of high melting point relative to the first alloy.

A further embodiment of any of the foregoing embodiments may additionally and/or alternatively include: the at least one first alloy comprising about 21.25-22.75 chromium, about 5.7-6.3 aluminum, about 11.5-12.5 cobalt, about 5.7-6.3 silicon, boron in an amount no greater than 1.0 weight percent, and a balance of nickel plus impurities if any; and the at least one second alloy comprises about 4.75-10.5 chromium, about 5.5-6.7 aluminum, up to about 13 weight percent cobalt, about 3.75-9.0 tantalum, about 1.3-2.25 molybdenum, about 3.0-6.8 tungsten, about 2.6-3.25 rhenium, up to about 0.02 boron, about 0.05-2.0 hafnium, up to about 0.14 carbon, up to about 0.35 zirconium, and a balance of nickel plus impurities if any.

A further embodiment of any of the foregoing embodiments may additionally and/or alternatively include a boron content of the first alloy being at least 0.30 weight percent greater than a boron content, if any, of the second alloy.

A further embodiment of any of the foregoing embodiments may additionally and/or alternatively include: the at least one first alloy comprises no more than 1.0 weight percent of any other individual element; and the at least one second alloy comprises no more than 1.0 weight percent of any other individual element.

A further embodiment of any of the foregoing embodiments may additionally and/or alternatively include: the matrix having a characteristic thickness T₂ of 0.10-0.50 millimeters; and the self-braze material having a characteristic thickness T₁ of 0.20-2.5 millimeters.

A further embodiment of any of the foregoing embodiments may additionally and/or alternatively include the applied combination consisting of the self-braze material, the abrasive, and the matrix.

A further embodiment of any of the foregoing embodiments may additionally and/or alternatively include forming the combination by: slurry plating the abrasive and one or more components of the matrix to a first face of a sheet of the self braze-material; and cutting the plated sheet.

A further embodiment of any of the foregoing embodiments may additionally and/or alternatively include forming the sheet by: mixing powders of at least two different alloys; and sintering the mixture.

A further embodiment of any of the foregoing embodiments may additionally and/or alternatively include the slurry plating comprising nickel and/or cobalt entrapment plating of CrAlY particulate and nickel and/or cobalt entrapment plating of the abrasive.

A further embodiment of any of the foregoing embodiments may additionally and/or alternatively include an article formed by the method.

A further embodiment of any of the foregoing embodiments may additionally and/or alternatively include the article being a turbine blade and wherein the combination is applied to a tip surface of an airfoil of the blade.

Another aspect of the disclosure involves an article comprising: a metallic substrate; a layer bonded to the substrate; and a matrix bonded to the material and at least partially embedding an abrasive. At least a portion of the material has a composition comprising, in weight percent: cobalt 2.5-13.5; chromium 12-27; aluminum 5-7; yttrium 0.0-1.0; hafnium 0.0-1.0; silicon 1.0-3.0; tantalum 0.0-4.5; tungsten 0.0-6.5; rhenium 0.0-2.0; molybdenum 0.1-1.0; and the balance nickel plus impurities, if any.

A further embodiment of any of the foregoing embodiments may additionally and/or alternatively include the article being a turbine blade and wherein the material is along a tip surface of an airfoil of the blade.

The details of one or more embodiments are set forth in the accompanying drawings and the description below. Other features, objects, and advantages will be apparent from the description and drawings, and from the claims.

BRIEF DESCRIPTION OF THE DRAWINGS

FIG. 1 is a schematic cross-section of an abrasive preform exploded away from a substrate to which it is being applied.

Like reference numbers and designations in the various drawings indicate like elements.

DETAILED DESCRIPTION

FIG. 1 shows an abrasive preform 20. The preform may have a planform (footprint) cut to correspond to the area of a surface 22 substrate 24 to which it is to be applied. Exemplary substrate surfaces are tip surfaces of airfoils of turbine blades for installation in gas turbine engines.

The preform has a base layer 30 having an inboard surface or face 32 and an outboard surface or face 34. Atop the outboard surface is an abrasive layer 40 having abrasive particles 42 at least partially embedded in a matrix 44.

The base layer thickness is shown as an essentially constant T₁. Measured thickness may be a mean, median, or modal value. The abrasive layer matrix thickness is shown as an essentially constant T₂ (e.g., allowing for variation adjacent abrasive particles). Exemplary T₁ is 0.25 mm, more broadly 0.20-2.5 mm or 0.20-1.0 mm. Such thickness T₁ may be chosen so as to bond to the substrate and provide environmental protection. Thicker values may serve for dimensional restoration (e.g., when tip substrate is worn). Exemplary T₂ is 0.25 mm, more broadly 0.10-0.50 mm or 0.15-0.40 mm. Such thickness T₂ may be chosen so as to be sufficient to bind the matrix. Thicker matrix may allow multiple layers of abrasive particles to improve life of abrasive.

The exemplary turbine blade substrate is a nickel-based superalloy, more particularly, having a single crystal (SX) structure.

The base layer comprises an oxidation-resistant braze material. It is capable of self-brazing to the substrate. For self-brazing, it comprises a mixture of alloys of at least two different compositions. At least one of the alloys is a relatively low melting point (low melt) alloy and at least one of the alloys is a relatively high melting point (high melt) alloy. These alloys may themselves be nickel-based superalloys. The low melt alloy may comprise a relatively higher content of one or more elements acting as melting point suppressants/depressants than does the high melt alloy. U.S. Pat. No. 8,075,662 (the '662 patent) of Minor et al., issued Dec. 13, 2011, the disclosure of which patent is incorporated by reference herein in its entirety as if set forth at length, discloses exemplary braze material formed of a mixture of powders of differing composition.

From the '662 patent, an exemplary high melting point alloy comprises, in weight percent, about 4.75-10.5 chromium, about 5.5-6.7 aluminum, up to about 13 weight percent cobalt, about 3.75-9.0 tantalum, about 1.3-2.25 molybdenum, about 3.0-6.8 tungsten, about 2.6-3.25 rhenium, up to about 0.02 boron, about 0.05-2.0 hafnium, up to about 0.14 carbon, up to about 0.35 zirconium, and a balance of nickel. Other elements may be present in impurity amounts (e.g., typically not more than 1.0 weight percent each and 3.0 weight percent aggregate). The term “about” as used in this description relative to compositions or other values refers to possible variation in the given value, such as normally accepted variations or tolerances in the art.

Similarly, an exemplary corresponding low melting point alloy comprises about 21.25-22.75 chromium, about 5.7-6.3 aluminum, about 11.5-12.5 cobalt, about 5.7-6.3 silicon, boron in an amount no greater than 1.0 weight percent, and a balance of nickel. Other elements may be present in impurity amounts (e.g., typically not more than 1.0 weight percent each and 3.0 weight percent aggregate). In further examples said boron may be present in 0.040-1.0 or 0.45-0.55 weight percent. Said boron may be at least 0.40 weight percent greater than a boron content of the high melting point alloy. An exemplary melting point of the high melt alloy is 2300° F. to 2500° F. (1260° C. to 1371° C.). An exemplary melting point of the low melt alloy is 2050° F. to 2200° F. (1121° C. to 1204° C.). An exemplary difference in alloy melting points is at least 50° C. or an exemplary 50° C. to 150° C. or 60° C. to 120° C.

Table I below provides two examples of powder combinations. The identified final alloys reflect the nominal averaging of the compositions based upon their weight percentages. As a practical matter, especially near the interfaces with the substrate and the matrix, inter-diffusion may cause departures from this theoretical value. The final actual composition is, however, effective to provide desired oxidation resistance.

TABLE I Exemplary Oxidation-Resistant Braze alloys % Ni Cr Al Co Ta Mo W Re Si B Hf Y High Melt #1 75 57 25 6 4 8 1 0.1 Lo Melt #1 25 53.5 22 6 12 6 0.5 Final Alloy #1 56.1 24.3 6.0 3.0 3.0 0.0 6.0 0.0 1.5 0.1 0.8 0.1 High Melt #2 55 63.3 7 6.2 7.5 6.5 1.5 5 3 0.15 Lo Melt #2 45 53.5 22 6 12 6 0.5 Final Alloy #2 58.9 13.8 6.1 9.5 3.6 0.8 2.8 1.7 2.7 0.2 0.1

Exemplary high melt to low melt weight ratios are between 50:50 and 85:15, more particularly, 55:45 to 80:20.

The oxidation resistance comes from optimized percentages of Cr, Al, Si, Hf, and Y and effectively prevents oxidation at temperatures up to at least 2150° F. (1177° C.) in engine operating conditions. Similar compositions to the resulting final alloys are found in U.S. Pat. No. 8,354,176 (the '176 patent) of Minor et al., issued Jan. 15, 2013, the disclosure of which patent is incorporated by reference herein in its entirety as if set forth at length. The '176 patent discloses an exemplary composition comprising, in weight percent, cobalt about 2.5-13.5, chromium about 12-27, aluminum about 5-7, yttrium about 0.0-1.0, hafnium about 0.0-1.0, silicon about 1.0-3.0, tantalum about 0.0-4.5, tungsten about 0.0-6.5, rhenium about 0.0-2.0, molybdenum about 0.1-1.0 and the balance nickel.

A more particular example is an exemplary composition comprising, in weight percent, cobalt 2.5-13.5, chromium 12-27, aluminum 5-7, yttrium 0.0-1.0, hafnium 0.0-1.0, silicon 1.0-3.0, tantalum 2.0-4.5, tungsten 2.0-6.5, rhenium 0.0-2.0, molybdenum 0.1-1.0 and the balance nickel.

Other elements may be present in impurity amounts (e.g., typically not more than 1.0 weight percent each and 3.0 weight percent aggregate). For example, among these will likely be residual boron from the low melt alloy and elements diffused in from the matrix, abrasive, or substrate. Some of such diffused elements may be localized to transition regions, leaving a core region/layer closer to the nominal composition formed by the two alloys.

Such material may have improved oxidation/corrosion resistance compared with a baseline standard second generation nickel-based superalloy (e.g., an alloy such as PWA1484 of United Technologies Corporation, Hartford Conn. and disclosed as the preferred example of U.S. Pat. No. 4,719,080 (the '080 patent) of Duhl et al., issued Jan. 12, 1988, and entitled “Advanced high strength single crystal superalloy compositions”, the disclosure of which patent is incorporated by reference herein in its entirety as if set forth at length). Similarly, such baseline superalloy may have superior oxidation and corrosion resistance to conventional braze materials. Accordingly, comparison to such a baseline may be used to distinguish relative oxidation and corrosion resistance.

In the '176 patent, an uncoated PWA 1484 substrate was used as the baseline and assigned a relative absolute life of exactly 1. It and inventive coating compositions were subject to oxidation and corrosion resistance tests.

In the '176 patent, a burner rig oxidation test was performed. In these tests, a coating was placed on a bar or coupon and mounted in a holder, in this case, a rotating spindle. The spindle rotated and was thrust into a flame for a period of time and withdrawn for a much shorter period of time, and after a number of these repetitive cycles, the oxidation was measured. The flame is a combustion product comprised of an ignited mixture of jet fuel and air. The speed of rotation of the spindle can vary from less than 400 rpm to more than 600 rpm. The samples were held in the flame for about 1 to 60 minutes, followed by removal for 1 to 5 minutes. Results were reported as a relative life, or as a ratio of life measured of the specimen over the life measured of a control. All tests were run at 2150° F. (1177° F.), although temperatures between 1800° F. (980° C.) and 2300° F. (1260° C.) can be used. The intent of this type of evaluation is to replicate the environment experienced in actual engines without having to perform the test using an actual engine.

In the '176 patent, coating identified as Composition One had a composition in weight percent of 3.0 cobalt, 24.3 chromium, 6.0 aluminum, 0.1 yttrium, 0.8 hafnium, 1.5 weight percent silicon, 3.0 tantalum, 6.0 tungsten, 0.0 rhenium, 0.0 molybdenum and the balance nickel. Substrates coated with Composition One had a relative absolute oxidation life value using the same test of approximately 2.2. In other words Composition One has a functioning oxidation life that was more than twice as long a functioning life as the base line uncoated substrate.

A coating identified as Composition Two had a composition in weight percent of 12.0 cobalt, 13.6 chromium, 6.1 aluminum, 0.0 yttrium, 0.8 hafnium, 2.7 silicon, 3.5 tantalum, 2.8 tungsten, 1.5 rhenium, 0.8 molybdenum and the balance nickel. Substrates coated with composition Two had a relative oxidation life value of approximately 1.4, or almost half again as long a functioning life compared to the baseline alloy substrate against which it is compared.

Accordingly, by this test, the two tested compositions had oxidation lives exceeding that of the baseline, more particularly, at least 1.3 times the baseline. Depending on conditions, preferred coatings may have such oxidation lives of at least 1.5 times the baseline or up to 2.5 times the baseline if not more.

In the '176 patent, an additional method of assessing the oxidation life of a coating system is via cyclic furnace oxidation testing. This Furnace Cycle Oxidation Weight Change Measurement test was conducted, comparing the same uncoated Ni based superalloy substrate with a substrate coated with Composition One as set forth above. In this test, specimens of each were raised and lowered into an air furnace, with the furnace maintained at the same temperature for all of the tests. No jet fuel was used. After a certain number of cycles, the specimens were removed, and weighed and the data recorded. Cycling the same specimens was resumed.

The uncoated Ni based superalloy substrate lost considerable weight after a relatively few cycles. Specifically, the uncoated superalloy substrates lost 65 mg/cm² in 100 cycles. Substrates coated with Composition One only lost 8 mg/cm² in over 360 cycles. This is a significant improvement in oxidation resistance showing that the addition of the coating increases the oxidation durability of the components, thus, allowing parts to be in service for substantially longer periods of time. Thus, by this test, material loss may be reduced by an exemplary at least 50%, more particularly, at least 75% relative to the baseline.

In the '176 patent, a corrosion test was performed. The test comprised taking a selected number of samples, exposing them to a salt solution, placing them in the elevated temperature in a static air furnace, without jet fuel or other combustion materials, for a period of time, such as a full day. Other time periods of less than twelve hours to more than thirty six hours can be used. The samples are removed, more salt solution is applied, and the samples were reinserted in the environment. At selected periods of time, one of the samples were removed from the test apparatus and the effects of corrosion were evaluated.

Substrates coated with Composition Two identified above were compared to the standard uncoated second generation Ni based superalloy. Four coupons of each were subjected to this test. One of the four coupons was removed and evaluated at each of the times shown in Table II. Samples were metallographically prepared, and the depth of attack through the coating was measured.

Presented below in Table II are the results of this test which was run at 1650° F. (899° C.)

TABLE II Hot Corrosion Test Depth of attack (mils (micrometers)) Uncoated Substrate with Time Ni-based Composition Two (hours) superalloy Coating 25 0.9 (23)  0.5 (13) 100 2.3 (58)  0.5 (13) 500 5.6 (142) 2.0 (51) 1000 9.8 (249) 2.7 (69)

As can be seen in Table II, the resistance of the coupons coated with Composition Two to hot corrosion was much greater, and was almost as effective at 1000 hours as the uncoated superalloy at 100 hours. Thus, exemplary improvement may be characterized as having a greater time to achieve the same level of corrosion than the baseline does at 100 hours, more particularly, at least 50% more time or at least doubling or tripling or quadrupling.

The matrix comprises an MCrAlY. Matrix material is chosen so to provide oxidation resistance and corrosion resistance. An exemplary MCrAlY is Ni/Co plating with Cr, Al, and Y. More particularly, an exemplary MCrAlY comprises, by weight 50-70% Ni and/or Co. The CrAlY may be an exemplary 30-50%. Impurity or other levels of components are possible. Of the Cr, Al, and Y, an exemplary proportion is 64-75% Cr, 24-35% Al, and 1-3% Y. An exemplary narrower range is 67-73% Cr, 27-33% Al, and 1-2% Y.

The exemplary abrasive is a cubic boron nitride (CBN). Exemplary CBN is particles of characteristic size 3.5 to 9 mils (0.09 to 0.23 mm). The exemplary abrasive quantity is 20-40% volume percent relative to combined abrasive and matrix.

In a process of manufacture, sheets (plates) of the braze material are prepared by mixing the powders in desired weight ratio and pre-sintering them into an essentially fully dense plate. Exemplary sintering is by heating a mixture in a vacuum atmosphere at elevated temperature (e.g., 2100° F. to 2300° F. (1149° C. to 1260° C.)) for exemplary times of 1-10 hours. The sintering does not fully homogenize the alloy but may cause inter-diffusion at boundaries between particles. For example, it may create a near homogeneous alloy with discrete low melting areas. This is effective to leave particles of the low melt alloy with sufficient quantity of the melting point suppressant to bond the prealloyed mixture to the substrate at a later stage in the processing.

The matrix and abrasive may be co-applied to the outboard surface 34. Exemplary co-application is a plating process. Exemplary plating is a slurry plating in which discrete states of abrasive, CrAlY, and nickel and/or cobalt (hereafter collectively Ni/Co) are applied. This is followed by an interdiffusion discussed below. In one exemplary process, the plating is an entrapment plating process wherein the Ni/Co is used in one or more stages to entrap particles of the other components. In one example, a first stage involves Ni/Co entrapment plating of a first amount of the CrAlY powder to the substrate. The second stage involves Ni/Co entrapment plating of the abrasive (e.g., CBN) atop the first plating. A third stage involves Ni/Co entrapment plating of a second amount of CrAlY powder around the abrasive particles applied in the second stage. The relatively large size of abrasive particles compared with the CrAlY particles means that there will be a high degree of protrusion of the abrasive particles applied during the second stage compared with CrAlY particles applied during the first stage.

After plating, there may be a heat treatment to cause the diffusion to at least partially homogenize the MCrAlY and bond it to the braze material. Alternatively, this result may be achieved during the final bonding. The exemplary heat treatment is to 1900° F. to 2000° F. (1038° C. to 1204° C.). If performed, this heat treatment leaves the material of the base layer 32 still having discrete low and high melt phases in order to allow a sufficient quantity of the melting point suppressant to bond the prealloyed mixture to the substrate at a later stage in the processing.

Preforms may then be cut (e.g., laser cut or water jet cut) from the sheet. In the blade tip example, these may have airfoil-shaped planforms (or planforms formed as perimeter portions of airfoil shapes for tips having squealer pockets).

The preforms may then be brazed to the substrates. Exemplary brazing comprises applying the preforms with surfaces 32 supported atop substrate surface 22. The preforms may initially be temporarily/partially secured by one or more appropriate means. For example, a tack weld at one location along the perimeter may be effective. Alternatively, an adhesive may be used. Such adhesive may evaporate or melt away in subsequent heat. The exemplary brazing occurs without the use of any additional flux or chemical treatment. The substrates may then be heated (e.g., in a furnace) to a temperature effective to braze the preform to the substrate. Exemplary heating is accomplished in a vacuum furnace or by induction heating. Exemplary heating is at 2100° F. to 2300° F. (1149° C. to 1260° C.) for a period of at least one minute, more particularly, an exemplary 5-10 minutes. A short time above the solidus of the pre-alloyed plate will allow high temperature diffusion braze bonding of environmental resistant braze while not affecting the plated CBN/MCrAlY matrix. This allows the use of more preferred/durable chemistries to be used below the CBN/MCrAlY matrix. This may allow a sufficient quantity of the melting point suppressant to bond and diffuse the prealloyed mixture to the substrate without affecting the structure of the plated CBN in MCrAlY matrix.

The use of “first”, “second”, and the like in the following claims is for differentiation within the claim only and does not necessarily indicate relative or absolute importance or temporal order. Similarly, the identification in a claim of one element as “first” (or the like) does not preclude such “first” element from identifying an element that is referred to as “second” (or the like) in another claim or in the description.

Where a measure is given in English units followed by a parenthetical containing corresponding SI or other units, the parenthetical's units are a conversion and should not imply a degree of precision not found in the English units.

One or more embodiments have been described. Nevertheless, it will be understood that various modifications may be made. For example, when applied to an existing baseline configuration, details of such baseline may influence details of particular implementations. Accordingly, other embodiments are within the scope of the following claims. 

What is claimed is:
 1. A method for applying an abrasive, the method comprising: applying, to a substrate, the integral combination of: a self-braze material; an abrasive; and a matrix in which the abrasive is at least partially embedded; and heating to cause the self-braze material to braze to the substrate, the heating leaving at least a portion of the self-braze material with a composition comprising, in weight percent: cobalt 2.5-13.5; chromium 12-27; aluminum 5-7; yttrium 0.0-1.0; hafnium 0.0-1.0; silicon 1.0-3.0; tantalum 0.0-4.5; tungsten 0.0-6.5; rhenium 0.0-2.0; molybdenum 0.1-1.0; and the balance nickel.
 2. The method of claim 1 wherein: said portion of the self-braze material has said composition comprising, in weight percent: cobalt 2.5-13.5; chromium 12-27; aluminum 5-7; yttrium 0.0-1.0; hafnium 0.0-1.0; silicon 1.0-3.0; tantalum 2.0-4.5; tungsten 2.0-6.5; rhenium 0.0-2.0; molybdenum 0.1-1.0; and the balance nickel.
 3. The method of claim 1 wherein: said composition has no more than 1.0 weight percent of any other individual element.
 4. The method of claim 1 wherein: said composition has no more than 3.0 weight percent of all other individual elements combined.
 5. The method of claim 1 wherein: the matrix comprises an MCrAlY; and the abrasive comprises cubic boron nitride.
 6. The method of claim 1 wherein the self-braze material comprises a sintered sheet of: at least one first alloy of low melting point relative to the substrate; and at least one second alloy of high melting point relative to the first alloy.
 7. The method of claim 6 wherein: the at least one first alloy comprises about 21.25-22.75 chromium, about 5.7-6.3 aluminum, about 11.5-12.5 cobalt, about 5.7-6.3 silicon, boron in an amount no greater than 1.0 weight percent, and a balance of nickel plus impurities if any; and the at least one second alloy comprises about 4.75-10.5 chromium, about 5.5-6.7 aluminum, up to about 13 weight percent cobalt, about 3.75-9.0 tantalum, about 1.3-2.25 molybdenum, about 3.0-6.8 tungsten, about 2.6-3.25 rhenium, up to about 0.02 boron, about 0.05-2.0 hafnium, up to about 0.14 carbon, up to about 0.35 zirconium, and a balance of nickel plus impurities if any.
 8. The method of claim 7 wherein: a boron content of the first alloy is at least 0.30 weight percent greater than a boron content, if any, of the second alloy.
 9. The method of claim 7 wherein: the at least one first alloy comprises no more than 1.0 weight percent of any other individual element; and the at least one second alloy comprises no more than 1.0 weight percent of any other individual element.
 10. The method of claim 1 wherein: the matrix has a characteristic thickness T₂ of 0.10-0.50 millimeters; and the self-braze material has a characteristic thickness T₁ of 0.20-2.5 millimeters.
 11. The method of claim 1 wherein: the applied combination consists of the self-braze material, the abrasive, and the matrix.
 12. The method of claim 1 further comprising forming the combination by: slurry plating the abrasive and one or more components of the matrix to a first face of a sheet of the self braze-material; and cutting the plated sheet.
 13. The method of claim 12 further comprising forming the sheet by: mixing powders of at least two different alloys; and sintering the mixture.
 14. The method of claim 12 wherein: the slurry plating comprises nickel and/or cobalt entrapment plating of CrAlY particulate; and nickel and/or cobalt entrapment plating of the abrasive.
 15. An article formed by the method of claim
 1. 16. The article of claim 15 being a turbine blade and wherein the combination is applied to a tip surface of an airfoil of the blade.
 17. An article comprising: a metallic substrate; a layer bonded to the substrate; and a matrix bonded to the material and at least partially embedding an abrasive, wherein: at least a portion of the material has a composition comprising, in weight percent: cobalt 2.5-13.5; chromium 12-27; aluminum 5-7; yttrium 0.0-1.0; hafnium 0.0-1.0; silicon 1.0-3.0; tantalum 0.0-4.5; tungsten 0.0-6.5; rhenium 0.0-2.0; molybdenum 0.1-1.0; and the balance nickel plus impurities, if any.
 18. The article of claim 17 being a turbine blade and wherein the material is along a tip surface of an airfoil of the blade. 